Gas turbine engine having bleed apparatus with dynamic pressure

Details Gas turbine engine having bleed apparatus with dynamic pressure Gas turbine engine having bleed apparatus with dynamic pressure

1977-12-27

1980-12-02

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

415115, F01D 518

Patent

active

042368693

ABSTRACT:
A gas turbine engine has conduits leading from the compressor to the turbine for bleeding a portion of compressor air through the turbine blades for cooling or other purposes. A radial pump in the conduits formed by a tangential accelerator and a rotating diffuser transmits the air from the non-rotating environment in the engine to the rotating environment of the turbine rotor. The tangential accelerator accelerates the bleed air to a tangential speed higher than that of the rotor, and the radial diffuser is designed to recover the dynamic pressure or relative velocity of the air over the rotor.

REFERENCES:
patent: 2951340 (1960-09-01), Howald
patent: 2988325 (1961-06-01), Dawson
patent: 3565545 (1971-02-01), Bobo et al.
patent: 3768921 (1973-10-01), Brown et al.
patent: 3791758 (1974-02-01), Jenkinson
patent: 3826084 (1974-07-01), Branstrom et al.
patent: 3936215 (1976-02-01), Hoff
patent: 3980411 (1976-08-01), Crow
patent: 4113406 (1978-09-01), Lee et al.

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